US5623821A - Turbojet equipped with a deicing system on the intake case - Google Patents
Turbojet equipped with a deicing system on the intake case Download PDFInfo
- Publication number
- US5623821A US5623821A US08/509,054 US50905495A US5623821A US 5623821 A US5623821 A US 5623821A US 50905495 A US50905495 A US 50905495A US 5623821 A US5623821 A US 5623821A
- Authority
- US
- United States
- Prior art keywords
- radial arms
- annular waveguide
- turbojet
- waveguide
- radial
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
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- 230000005540 biological transmission Effects 0.000 description 4
- 238000010438 heat treatment Methods 0.000 description 4
- 239000004593 Epoxy Substances 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000011521 glass Substances 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 239000000463 material Substances 0.000 description 2
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Images
Classifications
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B6/00—Heating by electric, magnetic or electromagnetic fields
- H05B6/64—Heating using microwaves
- H05B6/80—Apparatus for specific applications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
- B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
- B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
-
- H—ELECTRICITY
- H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
- H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
- H05B2214/00—Aspects relating to resistive heating, induction heating and heating using microwaves, covered by groups H05B3/00, H05B6/00
- H05B2214/02—Heaters specially designed for de-icing or protection against icing
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the invention relates to deicing systems for air navigation and in particular on aircraft turbojets or turbojet engines.
- certain parts of the turbojet such as the intake case, are exposed to problems caused by ice.
- the turbojet air intake is liable to be exposed to icing phenomena.
- the turbojet intake case, its radial arms, its cowls and its mobile flaps can be subject to an accumulation of ice, which obviously leads to a deterioration of the aerodynamic performance characteristics of the turbojet.
- the ice blocks which are then detached from these different components can damage the rotor of the turbojet located in the downstream direction, when they are sucked into the latter.
- French patent application FR-A-2 346 217 discloses a system for deicing by microwaves composite material helicopter blades. Reference is also made therein to the possibility of applying this procedure to aircraft.
- the object of the present invention is to apply such a heating method to the upstream parts of an aircraft turbojet in order to prevent icing on the case, radial arms, cowl and flaps.
- the invention mainly relates to a turbojet having an air intake case equipped with dielectric composite material radial arms extending between an outer, annular structure and an inner, central structure.
- This turbojet is equipped with means for deicing the radial arms by microwaves located on the central structure having a microwave generator fixed to the intake case, means for transmitting the energy supplied by the generator, means for distributing the energy in the arms to be heated constituted by an annular waveguide placed within said central structure and against its outer wall and means for coupling the arms with the energy transmission means.
- the deicing means are located on the outer structure, in the form of at least one annular waveguide placed on the outer structure, the microwave generator also being placed on said outer structure.
- the waveguide has first transverse openings on its inner wall and in each of said openings is placed the outer end of one of the radial arms, said outer end being fixed in the outer structure.
- the radial arms are fixed to the outer structure by means of pins traversing the outer end of the radial arms in the waveguide and constituting coupling means.
- the waveguide is still annular and has second transverse openings on its inner surface issuing between and alongside radial arms in order to permit the microwaves to pass out of the waveguide and be oriented towards the outer surfaces of the radial arms.
- the waveguide has third transverse openings on its outer surface in each of which is placed the inner end of one of the arms, said inner end being fixed to the central structure.
- the coupling means are constituted by fixing bolts for fixing the waveguide to the central structure.
- the coupling means When each radial arm is equipped with a mobile flap, the coupling means also comprise coaxial conductor cables connecting the trailing edge of each radial arm to the leading edge of the corresponding mobile flap.
- the cowl of the inner, central structure is internally metallized.
- FIG. 1 The front part of a turbojet according to the invention, on which are shown the three embodiments thereof.
- FIGS. 2A & 2B In partial section, the first embodiment of the invention.
- FIGS. 3A & 3B In partial section, the second embodiment of the invention.
- FIGS. 4A & 4B In partial section, the third embodiment of the invention.
- FIG. 5 The fixing of a radial arm according to the first embodiment of the invention.
- FIG. 6 The coupling between a mobile flap and its corresponding radial arm.
- FIG. 7 A diagram of a possible distribution of waves in the first two embodiments of the invention.
- the intake of a turbojet or turbojet engine inter alia comprises radial arms 1 fixed between an outer, annular structure 10 and a central structure 20.
- Each of the radial arms is extended by a flap 2 mobile in rotation about a spindle 2a perpendicular to the turbojet axis.
- the air flow penetrating the turbojet between each radial arm 1 is consequently conditioned for its use downstream in the turbojet.
- FIG. 1 Certain of the elements of the main embodiments of the invention are shown in FIG. 1.
- a outside, annular waveguide 11 placed on the outer surface 13 of the outer sleeve 12 constituting the outer structure 10 and the inner surface of the outside, annular waveguide 11.
- This waveguide 11 has two series of slots, whereof the outer slots 14 issue between the radial arms 1.
- the microwaves routed in the waveguide 11 then pass out along the radial arms 1 and act by electromagnetic energy dissipation in the water droplets or ice particles covering the surfaces of the radial arms 1.
- a first microwave generator 15 is shown at the bottom of FIG. 1 facing the first, annular waveguide 11.
- a second microwave generator 25 issues into a inside, annular waveguide 21 placed against the inner surface 23 of the cowl 22 of the central structure 20.
- This inside, annular waveguide 21 has equivalent slots to the outside, annular waveguide 11 in order to transmit electromagnetic energy to the radial arms 1 in the same way.
- each radial arm 1 is fixed in the outside, annular waveguide 11 and on the central structure 20.
- the outer end 4 of each radial arm 1 is placed within the outside, annular waveguide 11 by means of a first series of slots made in the annular sleeve 12.
- a pin 5 makes it possible to lock said arrangement by traversing the outer end 4 of the radial arm within the outside, annular waveguide 11.
- each pin 5 constitutes a coupling means between a radial arm, which is a means for distributing energy on the elements to be deiced and the outside, annular waveguide 11, which is a transmission means.
- FIG. 2A the radial arm 1 is shown with two mixed lines, symbolizing its walls 6.
- An ice layer 7 has accumulated against the radial arm 1.
- An arrow chain 8 symbolizes the routing of the microwaves, which penetrate, by means of the outer end 4 of the radial arm 1, the interior of the outside, annular waveguide 11, so as to then traverse the entire wall 6 of the radial arm 1 and encroach on the ice particles 7.
- FIG. 2B shows the same components viewed from the side. It can be seen that once the microwaves have arrived at the inner end 9 of the radial arm 1, they can be discharged by the inside waveguide 21 and transmitted to the cowl 22 by means of bolts 24 serving as electromagnetic energy coupling means. Thus, the entire outer surface 23 of the cowl 22 can be subject to the same electromagnetic energy conditions with the same deicing aim.
- FIG. 2B also shows coaxial conductor cables 30 in interrupted line form, which connect the trailing edge 1F of the radial arm 1 to the leading edge 2A of the flap 2.
- the walls 6 of the radial arms 1 are made from composite materials with a dielectric coating (e.g. of epoxy glass), so as to serve as surface waveguides and electromagnetic energy distribution means.
- a dielectric coating e.g. of epoxy glass
- FIG. 3B shows in section said same second solution. It is completed by a series of arrows 16 symbolizing the path of the microwaves. It should be noted that they could also be oriented along the outer surfaces of the flaps 2.
- the slots 14 of said second series act as conductivity holes, as in a slot antenna system, in order to form a wave beam enveloping the components to be deiced.
- the coaxial conductor cables 30 between the radial arms 1 and the flaps 2 can also be retained.
- the slots, lengths and widths of the slots 14 are dimensioned as a function of the emission frequency of the microwaves used. It should be noted that this frequency can be adapted so as to be in a range 2 to 30 GHz, in order to obtain a better heat dissipation efficiency in the ice or in order to reduce the radiation in the engine.
- FIG. 7 explains the case where, in the first two solutions, several microwave generators are provided for supplying a single circumference of annular waveguides 11. If four of these are used, they are distributed at 90° intervals about the axis of the turbojet and each ensures the distribution of the microwaves over a quarter of the radial arms.
- FIG. 4A shows an outer sleeve 34 constituting the outer structure 10 and having slots in which are located the outer ends 33 of the radial arms 1.
- the central structure 20 has an inner, annular waveguide 21.
- Its outer wall 35 has a series of slots, in each of which is inserted an inner end 32 of a radial arm 1.
- a fixing pin makes it possible to lock the radial arm 1 in said inner, annular waveguide 21, in a manner identical to the fixing described in FIGS. 2A and 2B, as well as in FIG. 5.
- a wave generator 25 is provided, as well as a transverse waveguide 26, so as to complete the means for transmitting microwaves to the radial arms 1.
- bolts 24 for fixing the inner, annular waveguide 21 to the cowl 22. These bolts 24 also serve as electromagnetic coupling means between the cowl 22 and the inner, annular waveguide 21.
- FIG. 5 explains a fixing example, like that of the first embodiment (cf. FIGS. 2A and 2B). It is possible to see therein the outside, outer, annular waveguide 11, in which is placed the outer end 4 of a radial arm 1. Two fixing pins 5 traverse said outer end 4 in order to ensure the locking of the assembly, but also the electromagnetic coupling.
- the arm is positioned within said outside, annular waveguide 11 by means of a support 43 resting on the inner surface 18 of the annular waveguide 11 facing the radial arm 1.
- This support 43 can be supplemented by two positioning sides 44, placed on either side of the outer end 4 of the radial arm 1.
- the structure of the radial arm 1 is preferably half hollow.
- two or three longitudinal cavities 41, 42 can be provided within the radial arm 1.
- the latter is preferably made from a dielectric composite material, e.g. epoxy glass.
- the outside, outer, annular waveguide 11 is also preferably made from a composite material, but its outer surface 19 is metallized in order to aid the guiding of the electromagnetic waves.
- the microwave transmission means between the arms 1 and the mobile flaps 2 are preferably constituted by several coaxial, conductor cables 30. If necessary, the latter can be in the form of a loop 36 located in a cavity 1C of the radial arm 1 and a cavity 2c of the mobile flap 2.
- the frequency of the microwaves can be in a range 2 to 30 GHz, in order to obtain a better effectiveness of the heat dissipation in the ice, or in order to reduce the parasitic radiation in the engine. If necessary, it is possible to use in the design of the components to be deiced, materials able to absorb microwaves and able to heat the structure to a greater or lesser extent in order to prevent a possible refreezing of the water droplets.
- the energy consumed is relatively low, because virtually only the ice is heated.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Constitution Of High-Frequency Heating (AREA)
Abstract
Description
Claims (8)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR9410102 | 1994-08-18 | ||
FR9410102A FR2723761B1 (en) | 1994-08-18 | 1994-08-18 | TURBOREACTOR EQUIPPED WITH A DEFROST SYSTEM ON THE INPUT HOUSING |
Publications (1)
Publication Number | Publication Date |
---|---|
US5623821A true US5623821A (en) | 1997-04-29 |
Family
ID=9466363
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US08/509,054 Expired - Lifetime US5623821A (en) | 1994-08-18 | 1995-07-31 | Turbojet equipped with a deicing system on the intake case |
Country Status (3)
Country | Link |
---|---|
US (1) | US5623821A (en) |
FR (1) | FR2723761B1 (en) |
GB (1) | GB2292422B (en) |
Cited By (30)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6206325B1 (en) | 1998-09-18 | 2001-03-27 | Sunlase, Inc. | Onboard aircraft de-icing using lasers |
WO2001074661A1 (en) * | 2000-04-03 | 2001-10-11 | Forschungszentrum Karlsruhe Gmbh | Compact microwave system for deicing and/or preventing icing of the outer surface of hollow or shell structures subject to meteorological influences |
WO2001074662A1 (en) * | 2000-04-03 | 2001-10-11 | Forschungszentrum Karlsruhe Gmbh | Compact millimeter wave technical system for de-icing and/or preventing the formation of ice on the outer surface of hollow or shell structures exposed to meteorological influences |
WO2002086298A2 (en) * | 2001-04-24 | 2002-10-31 | Honeywell International Inc. | Heating device and method for deployable ram air turbine |
US6593547B1 (en) | 2000-11-30 | 2003-07-15 | Pacific Scientific Electro Kinetics Division | Air gap deicing device |
US20060037303A1 (en) * | 2004-08-18 | 2006-02-23 | Thompson Robert G | Inlet muff anti-icing system for an auxiliary power unit |
US20060280600A1 (en) * | 2005-05-31 | 2006-12-14 | United Technologies Corporation | Electrothermal inlet ice protection system |
US20080092516A1 (en) * | 2006-10-21 | 2008-04-24 | Rolls-Royce Plc | Engine arrangement |
US20080307769A1 (en) * | 2007-06-18 | 2008-12-18 | Honeywell International, Inc. | Gas turbine engine anti-ice formation device and system |
US20090060720A1 (en) * | 2007-08-31 | 2009-03-05 | General Electric Company | Slipring bushing assembly for moveable turbine vane |
US20090060721A1 (en) * | 2007-08-31 | 2009-03-05 | General Electric Company | Bushing and clock spring assembly for moveable turbine vane |
US20090154522A1 (en) * | 2007-12-18 | 2009-06-18 | Weston Aerospace Limited | Temperature sensor and method for measuring temperature |
US20090241509A1 (en) * | 2008-03-25 | 2009-10-01 | Isaac Jon Hogate | Turbine engine inlet strut deicing |
US20100101206A1 (en) * | 2007-03-19 | 2010-04-29 | Turbomeca | Device for de-icing the air intake of a gas turbine |
US20100296910A1 (en) * | 2009-05-21 | 2010-11-25 | Robert Lee Wolford | Thermal system for a working member of a power plant |
US20100326041A1 (en) * | 2009-06-30 | 2010-12-30 | Wayne Garcia Edmondson | Heated guide vane |
US20100329836A1 (en) * | 2009-06-30 | 2010-12-30 | Wayne Garcia Edmondson | Method of operating a heated guide vane assembly |
US20110099970A1 (en) * | 2009-11-03 | 2011-05-05 | General Electric Company | System for ice and/or frost prevention using guided wave energy |
US8210825B2 (en) | 2007-05-11 | 2012-07-03 | Honeywell International Inc. | Heated engine nose cone using spiral channels |
US20120174595A1 (en) * | 2011-01-06 | 2012-07-12 | Francisco Jay M | Arrangement for maintaining flow to an air inlet of an auxiliary power unit assembly |
US20140144519A1 (en) * | 2012-11-23 | 2014-05-29 | Airbus Operations (Sas) | Aircraft nacelle comprising a reinforced connection between an air intake and a powerplant |
CN104507810A (en) * | 2012-07-30 | 2015-04-08 | 涡轮梅坎公司 | Helicopter engine air intake with improved bypass flow |
FR3025834A1 (en) * | 2014-09-11 | 2016-03-18 | Turbomeca | DEFROSTING SYSTEM OF ENGINE AIR INPUT |
US20180031002A1 (en) * | 2016-08-01 | 2018-02-01 | United Technologies Corporation | Annular heatshield |
US10781707B2 (en) | 2018-09-14 | 2020-09-22 | United Technologies Corporation | Integral half vane, ringcase, and id shroud |
US10794200B2 (en) | 2018-09-14 | 2020-10-06 | United Technologies Corporation | Integral half vane, ringcase, and id shroud |
US11421547B2 (en) * | 2020-01-06 | 2022-08-23 | Rohr, Inc. | Thermal-anti-icing system with microwave system |
US20230348073A1 (en) * | 2022-04-28 | 2023-11-02 | Rohr, Inc. | Ice protection system including frequency dependent susceptor |
US12012212B2 (en) | 2021-06-30 | 2024-06-18 | Rohr, Inc. | Microwave thermal anti-icing system for aircraft acoustic structure |
US12017779B2 (en) | 2021-06-30 | 2024-06-25 | Rohr, Inc. | Integrated microwave thermal anti-icing system |
Families Citing this family (8)
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DK0914276T3 (en) * | 1996-07-03 | 2003-12-08 | Lm Glasfiber As | Method and plant for de-icing blades of composite material |
FR2941998B1 (en) * | 2009-02-06 | 2011-03-11 | Gen Electric | SOCKET AND MOTOR SPRING ASSEMBLY FOR TURBINE MOBILE DRAW. |
CN103523235B (en) * | 2012-07-06 | 2015-12-02 | 哈尔滨飞机工业集团有限责任公司 | Aircraft engine nacelle inlet channel fairing |
CN103628984B (en) * | 2013-12-06 | 2015-07-08 | 中国电力工程顾问集团西南电力设计院有限公司 | Loop heating system for gas turbine anti-freezing device and working method of loop heating system |
FR3112368B1 (en) * | 2020-07-08 | 2022-08-05 | Safran Aircraft Engines | AIR INLET FOR AN AIRCRAFT TURBOMACHINE, AN AIRCRAFT TURBOMACHINE EQUIPPED WITH SUCH AN AIR INLET AND METHOD FOR MAINTAINING IT |
GB2599691A (en) * | 2020-10-09 | 2022-04-13 | Rolls Royce Plc | A heat exchanger |
GB2599693B (en) * | 2020-10-09 | 2022-12-14 | Rolls Royce Plc | A heat exchanger |
CN114576009B (en) * | 2022-03-16 | 2024-08-02 | 中国航发沈阳发动机研究所 | Waveguide fluid is inhaled to aeroengine import department |
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FR1016933A (en) * | 1948-11-18 | 1952-11-26 | Canadian Patents Dev | Anti-icing device, for compressors of aircraft turbo-engines |
FR1103223A (en) * | 1953-07-03 | 1955-10-31 | Armstrong Siddeley Motors Ltd | De-icing device for gas turbine aircraft engine |
BE686024A (en) * | 1965-09-03 | 1967-02-01 | ||
FR2346217A1 (en) * | 1976-04-01 | 1977-10-28 | System Dev Corp | DEFROSTING PROCESS AND DEVICE |
US4365131A (en) * | 1980-06-27 | 1982-12-21 | Hansman Jr Robert J | Microwave ice prevention system |
GB2136880A (en) * | 1983-03-18 | 1984-09-26 | Rolls Royce | Anti-icing of gas turbine engine air intakes |
US4863354A (en) * | 1987-10-07 | 1989-09-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Nose cowl for a turbojet engine shaft |
US5029440A (en) * | 1990-01-26 | 1991-07-09 | The United States Of America As Represented By The Secretary Of The Air Force | Acoustical anti-icing system |
US5061836A (en) * | 1990-01-18 | 1991-10-29 | United Technologies Corporation | Microwave deicing for aircraft engine propulsor blades |
GB2259287A (en) * | 1991-09-04 | 1993-03-10 | Rolls Royce Plc | Apparatus for and method of de-icing a surface |
Family Cites Families (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3341114A (en) * | 1966-03-04 | 1967-09-12 | Gen Electric | Anti-icing means |
-
1994
- 1994-08-18 FR FR9410102A patent/FR2723761B1/en not_active Expired - Lifetime
-
1995
- 1995-07-31 US US08/509,054 patent/US5623821A/en not_active Expired - Lifetime
- 1995-08-09 GB GB9516358A patent/GB2292422B/en not_active Expired - Fee Related
Patent Citations (10)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR1016933A (en) * | 1948-11-18 | 1952-11-26 | Canadian Patents Dev | Anti-icing device, for compressors of aircraft turbo-engines |
FR1103223A (en) * | 1953-07-03 | 1955-10-31 | Armstrong Siddeley Motors Ltd | De-icing device for gas turbine aircraft engine |
BE686024A (en) * | 1965-09-03 | 1967-02-01 | ||
FR2346217A1 (en) * | 1976-04-01 | 1977-10-28 | System Dev Corp | DEFROSTING PROCESS AND DEVICE |
US4365131A (en) * | 1980-06-27 | 1982-12-21 | Hansman Jr Robert J | Microwave ice prevention system |
GB2136880A (en) * | 1983-03-18 | 1984-09-26 | Rolls Royce | Anti-icing of gas turbine engine air intakes |
US4863354A (en) * | 1987-10-07 | 1989-09-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Nose cowl for a turbojet engine shaft |
US5061836A (en) * | 1990-01-18 | 1991-10-29 | United Technologies Corporation | Microwave deicing for aircraft engine propulsor blades |
US5029440A (en) * | 1990-01-26 | 1991-07-09 | The United States Of America As Represented By The Secretary Of The Air Force | Acoustical anti-icing system |
GB2259287A (en) * | 1991-09-04 | 1993-03-10 | Rolls Royce Plc | Apparatus for and method of de-icing a surface |
Cited By (50)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6206325B1 (en) | 1998-09-18 | 2001-03-27 | Sunlase, Inc. | Onboard aircraft de-icing using lasers |
WO2001074661A1 (en) * | 2000-04-03 | 2001-10-11 | Forschungszentrum Karlsruhe Gmbh | Compact microwave system for deicing and/or preventing icing of the outer surface of hollow or shell structures subject to meteorological influences |
WO2001074662A1 (en) * | 2000-04-03 | 2001-10-11 | Forschungszentrum Karlsruhe Gmbh | Compact millimeter wave technical system for de-icing and/or preventing the formation of ice on the outer surface of hollow or shell structures exposed to meteorological influences |
US6610969B2 (en) | 2000-04-03 | 2003-08-26 | Forschungszentrum Karlsruhe Gmbh | Compact microwave system for de-icing and for preventing icing of the outer surfaces of hollow or shell structures which are exposed to meterological influences |
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Also Published As
Publication number | Publication date |
---|---|
GB2292422B (en) | 1998-07-29 |
GB9516358D0 (en) | 1995-10-11 |
FR2723761A1 (en) | 1996-02-23 |
FR2723761B1 (en) | 1996-09-20 |
GB2292422A (en) | 1996-02-21 |
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